CN115697735A - Ventilation device for a vehicle heating and/or air conditioning system - Google Patents

Abstract

The invention relates to a ventilation device (100) for a vehicle heating, ventilation and/or air conditioning system (200), comprising at least one casing (110) comprising at least one wall (114) defining an internal volume (210) in which at least one radial thruster (120) capable of being rotated and at least one guide member (130) are received, the radial thruster (120) and the guide member (130) being configured to generate an air Flow (FA) having a general direction parallel to the axis of rotation (R) of the radial thruster (120) between an air inlet (126) of the radial thruster (120) and an air outlet (112) formed in the wall (114) of the casing (110) of the ventilation device (100), at least one portion of the wall (114) of the casing (110) being configured to straighten the air Flow (FA) at the outlet of the radial thruster (120), characterized in that the guide member (130) is configured to guide the air Flow (FA) towards the axis of rotation (R) of the radial thruster (120).

Description

Ventilation device for a vehicle heating and/or air conditioning system

The present invention relates to the field of heating and/or air conditioning systems intended to be integrated into motor vehicles, for example electrically propelled motor vehicles.

Motor vehicles conventionally comprise heating and/or air-conditioning systems for the thermal treatment of an air flow intended to be directed into the passenger compartment of the vehicle. These heating and/or air conditioning systems comprise at least one housing in which at least one heat exchanger and at least one ventilation device are accommodated. For example, a heat transfer fluid (i.e., a fluid capable of collecting, carrying, and delivering calories) is circulated in the heat exchanger. An air flow also passes through the heat exchanger, which by passing through the heat exchanger undergoes a temperature change before being directed to the passenger compartment in order to thermally treat the temperature of the passenger compartment.

In order to generate an air flow that can pass through the heat exchanger, heating and/or air conditioning systems conventionally comprise at least one ventilation device comprising at least one impeller housed in a casing, wherein the impeller is rotated by a moving part, which can also be housed in the casing. The ventilation device currently implemented comprises: an axial air inlet, i.e. an opening allowing an air flow into the ventilation device in a direction parallel or substantially parallel to the axis of rotation of the propeller of the ventilation device; and a radial air outlet at which the air flow exits from the impeller in a radial direction. In other words, such a ventilation device is conventionally arranged in a volute such that an air flow enters the ventilation device in a first direction and leaves the housing in a second direction perpendicular to the first direction.

A disadvantage of these ventilation devices is that they are particularly bulky due to the radial nature of the air flow leaving the device. Therefore, they cannot be easily installed in particularly limited ventilation systems.

For example, document KR 2014/0054655A describes a ventilation device in which the air flow circulates between the air inlet of the propeller and the outlet of the ventilation device in a general direction parallel to the axis of rotation of the propeller of the ventilation device. A disadvantage of the ventilation device described in this document is that the air flow easily exits the ventilation device via a peripheral portion of the outlet opening formed in the housing. In other words, the flow rate of the air flow measured in the peripheral portion of the air outlet opening formed in the housing of the ventilation device is larger than the flow rate of the air flow measured in the central portion of the air outlet opening. The air outlet opening of this type of ventilation device can be closed by an air filter. Thus, the flow difference between the peripheral portion and the central portion of the air outlet may lead to a non-optimal use of such an air filter, which may result in the air filter needing to be replaced more frequently than if the flow of the air flow is constant or substantially constant over the entire surface of the air outlet opening, i.e. in both the central portion and the peripheral portion of the air outlet opening.

The present invention is of this background and aims at solving at least the mentioned drawbacks by proposing a ventilation device which is less bulky than the prior art ventilation devices and in which the air flow has a substantially constant flow rate at all points of the air outlet opening.

The object of the present invention therefore relates to a ventilation device for a vehicle heating, ventilation and/or air conditioning system, comprising at least one casing comprising at least one wall defining an internal volume in which at least one radial impeller capable of being rotated and at least one guide member are housed, the radial impeller and the guide member being configured to generate an air flow having a general direction parallel to the axis of rotation of the radial impeller between an air inlet of the radial impeller and an air outlet opening formed in a wall of the casing of the ventilation device, wherein at least a portion of the wall of the casing is configured to straighten the air flow exiting the radial impeller. According to the invention, the guiding member is configured to guide the air flow towards the rotational axis of the radial thruster.

A "radial propeller" is understood to mean a propeller in which an air flow enters in a first direction, in this case parallel to the axis of rotation of the propeller, and exits in a second transverse direction, for example perpendicular to the axis of rotation of the propeller. In other words, within the meaning of the present invention, the radial thruster comprises an axial air inlet and a radial air outlet. By "at least a portion of the wall of the housing is configured to straighten the air flow" is understood to mean that the shape of the wall is designed such that, when the air flow leaves the radial thruster, it meets the portion of the wall of the housing so as to deviate the air flow in order to straighten it, i.e. to direct it towards the guiding member. Thus, the shape of the housing of the ventilation device together with the air flow guiding member accommodated in the ventilation device allows the air flow generated by the rotation of the radial propeller to be guided, so that the overall volume of the ventilation device is reduced compared to the ventilation device of the prior art. Thus, the air outlet of the ventilation device according to the invention may be placed in the axial extension of the radial thruster, which allows to reduce the radial volume of such a device. As a result, the ventilation device according to the invention can be mounted more easily in small vehicles, such as at least partially electrically propelled vehicles. For example, the radial pusher may be rotated by the moving member. Alternatively, the support of the moving part may be accommodated in the inner volume of the housing. The ventilation device according to the invention allows to obtain a homogeneous distribution of the air flow over the entire surface of the outlet opening, even in the presence of a support placed axially at the centre of the outlet opening formed in the wall of the casing, by tilting the air flow so as to enter a portion of the outlet opening formed in the wall of the casing through which the axis of rotation of the radial thruster passes.

According to the invention, the air flow guiding member may comprise a plurality of fixed blades arranged axially between the radial propeller and the air outlet opening. For example, the at least one fixed blade of the air flow guiding member comprises at least one outer end rigidly connected to a wall of the housing. Advantageously, each fixed vane of the air flow guiding member comprises an outer end rigidly connected to a wall of the housing.

According to one feature of the invention, the radial thruster comprises a plurality of movable blades, wherein each movable blade comprises an inner edge oriented towards the axis of rotation of the radial thruster and an outer edge oriented away from the inner edge, wherein at least one outer edge extends parallel to the axis of rotation of the radial thruster. Advantageously, the outer edge of each movable vane extends in a direction parallel to the axis of rotation of the radial thruster.

According to another feature of the invention, the inner radius of the radial thruster, measured in a plane perpendicular to the axis of rotation of the radial thruster, between the axis of rotation of the radial thruster and the inner edge of one of the movable blades of the radial thruster ranges between 36mm and 54 mm. For example, the outer radius of the radial thruster, measured in a plane perpendicular to the axis of rotation between the axis of rotation and the outer edge of one of the movable blades of the radial thruster, may range between 64mm and 96 mm.

Advantageously, the height of the inner edge of the movable blade, measured parallel to the axis of rotation of the radial thruster, is greater than the height of the outer edge of the movable blade, measured parallel to the axis of rotation of the radial thruster. For example, the ratio between the height of the inner edge of a movable blade of the radial propeller and the height of the outer edge of the movable blade of the radial propeller may be set to range between 1.1 and 1.9. For example, the height of the inner edge of a movable blade of a radial thruster may range between 36mm and 54mm, and the height of the outer edge of this same movable blade of a radial thruster may range between 29mm and 44 mm. Furthermore, the inner edge of a movable blade of the radial thruster and the outer edge of this movable blade of the radial thruster may take different positions along the axis of rotation of the radial thruster, i.e. with an offset with respect to each other.

More specifically, the movable blades of the radial thruster extend between a bowl of the thruster and an edge of the thruster, respectively, wherein the bowl of the thruster has a convex shape when seen from the movable blades of the radial thruster, wherein the height of the inner edge of the movable blades and the height of the outer edge of the movable blades are measured between the bowl of the thruster and the edge of the thruster, respectively, parallel to the axis of rotation of the radial thruster.

According to one feature of the invention, each movable blade of the radial thruster is defined by at least one upper line oriented towards the air inlet of the radial thruster and by at least one lower line oriented towards the air outlet opening formed in the wall of the casing, and the upper line of the at least one movable blade of the radial thruster has at least one first portion projecting from the edge of the radial thruster towards the axis of rotation of the radial thruster and a second portion covered by the edge of the radial thruster. Advantageously, all upper lines of the movable blades of the radial thruster have the first portion and the second portion. The bowl of the radial thruster is more specifically arranged to connect the lower line of the movable blades of the radial thruster. Advantageously, the bowl of the radial thruster may be closed, i.e. the bowl extends continuously between two successive movable blades. As a result, the entire air flow generated by the rotation of the radial propeller exits the radial propeller via the radial air outlet.

According to another feature of the invention, the housing of the ventilation device comprises at least one upper portion housing the radial thruster and a lower portion housing the guide member, wherein the upper portion comprises at least one first convex curvature when viewed from the axis of rotation of the radial thruster and at least one second concave curvature when viewed from the axis of rotation of the radial thruster, the first curvature covering the edge of the radial thruster and the second curvature being arranged facing the radial air outlet of the radial thruster. More specifically, the first curvature covers the edge of the radial thruster when viewed in a plane perpendicular to the rotation axis of the radial thruster. Similarly, in a plane perpendicular to the axis of rotation of the radial thruster, the second curvature is arranged facing the radial air outlet of the radial thruster. In other words, the second curvature of the upper portion of the casing is arranged such that the air flow exiting the radial thruster meets the second curvature such that the second curvature forms a portion of the casing configured to straighten the air flow exiting the radial thruster.

According to one feature of the invention, the air flow guiding member comprises a plurality of fixed blades, wherein at least one fixed blade of the air flow guiding member comprises a pressure surface and a suction surface connected together by a leading edge and a trailing edge, wherein the fixed blade comprises a cross-section extending between the leading edge and the trailing edge along a camber line when viewed in a plane perpendicular to a radially extending axis of the associated fixed blade, wherein the camber line is inscribed in a circle, wherein a first angle is formed between a tangent of the circle at the leading edge and the camber line at the leading edge, and a second angle is formed between a tangent of the circle at the leading edge and the camber line at the trailing edge, the first angle ranging between 3 ° and 10 °, and the second angle ranging between 79 ° and 128 °. For example, the fixed blades of the guide member may be arranged in a circular profile, wherein the center of the circular profile forms the center of the guide member. Advantageously, all the fixed vanes of the air flow directing member may be structurally identical.

According to one feature of the invention, the at least one fixed vane of the air flow guiding member comprises a first portion, a second portion and a third portion aligned in this order along the radially extending axis of the fixed vane towards the wall of the housing, wherein the ratio between the first angle and the second angle measured in the first portion ranges between 0.03 and 0.07, the ratio between the first angle and the second angle measured in the second portion ranges between 0.05 and 0.12 and the ratio between the first angle and the second angle measured in the third portion ranges between 0.02 and 0.07. Advantageously, the first, second and third portions are integrally formed, i.e. they form a single component which cannot be separated without damage to at least one of these portions.

According to the invention, the radial thruster can be rotated by at least one moving part, wherein the casing comprises at least one support able to house the at least one part for moving the radial thruster, and the guide means are interposed between the support able to house the at least one moving part and the wall of the casing. According to a particular example of application of the invention, the centre of the guide member and the centre of the support of the mobile part are coincident.

According to one embodiment of the invention, the air flow guiding member comprises a plurality of fixed blades, wherein at least one fixed blade of the air flow guiding member comprises at least one inner end rigidly connected to a support capable of accommodating the moving part and at least one outer end rigidly connected to a wall of the housing. In other words, it will be appreciated that the airflow directing member is fixed relative to the housing. Advantageously, all the fixed blades of the air flow guiding member may comprise an inner end rigidly connected to the support of the moving part and at least one outer end rigidly connected to a wall of the housing. Alternatively, the housing, the air flow guiding member and the support of the moving part may be unitary, i.e. form a single assembly which cannot be separated without causing damage to at least the housing, the air flow guiding member and/or the support.

Alternatively, the air filter may be arranged to face an air outlet opening formed in a wall of the housing. Advantageously, the air filter may close the air outlet opening of the housing. In other words, the air flow guiding member then allows the entire available surface of the air filter to be used by deviating the air flow leaving the radial thruster, thereby improving the efficiency and durability of the air filter.

Advantageously, the ventilation means comprise means for moving the radial thruster. For example, the means for moving the radial propeller may be a direct current motor comprising a drive shaft that can be accommodated in the hub of the radial propeller. It will thus be appreciated from the foregoing that the moving part is accommodated in the housing, if necessary, on a support provided for this purpose.

The invention also relates to a heating, ventilation and/or air-conditioning system for a vehicle, comprising at least one ventilation device as mentioned above, the system comprising at least one heat exchanger configured to exchange heat between an air flow generated by a radial propeller and a coolant. "Coolant" is understood to mean a fluid configured to carry calories and exchange calories with or without changing states.

Further features, details and advantages will become more apparent upon reading the following detailed description, which is provided for purposes of illustration, with reference to the various views of the invention shown in the following drawings:

fig. 1 schematically shows a part of an heating and/or air-conditioning system according to the invention comprising at least one ventilation device according to the invention;

fig. 2 shows a perspective view of a ventilation device according to the invention;

fig. 3 shows a perspective view of a radial thruster of a ventilation device according to the invention;

fig. 4 shows a perspective bottom view of an air flow guiding member of a ventilation apparatus according to the present invention;

fig. 5 shows a cross-section of the first segment of the fixed blade of the air flow guiding member shown in fig. 4 taken along a first transverse plane AA shown in fig. 4;

fig. 6 shows a cross section of the second segment of the fixed blade of the air flow guiding member shown in fig. 5 taken along a second transverse plane BB shown in fig. 4;

fig. 7 shows a cross-section of the third segment of the fixed vane of the air flow guiding member shown in fig. 5 taken along a third transverse plane CC shown in fig. 4;

fig. 8 shows a vertical cross-sectional view of the ventilation device according to the invention along the vertical plane DD shown in fig. 1.

The features, alternative embodiments, and various embodiments of the invention may be combined in various combinations as long as they are not incompatible or mutually exclusive with each other. In particular, alternative embodiments of the invention may be envisaged, which comprise only the set of features described below independently of the other features described, provided that this set of features is sufficient to provide technical advantages or to distinguish the invention from the prior art.

Fig. 1 schematically shows a part of a heating, ventilating and/or air conditioning system 200 according to the invention. The heating, ventilation and/or air conditioning system 200 (hereinafter "system 200") is intended to be integrated into a motor vehicle (e.g., an electrically propelled motor vehicle) to thermally treat an air flow FA before it is directed into a passenger compartment of the vehicle to thermally treat the passenger compartment. In other words, the air flow FA serves to cool or heat the passenger compartment of the vehicle. The system 200 according to the invention comprises: at least one housing 201 housing at least one heat exchanger 202 therein, configured to exchange heat between a coolant and an air flow FA intended to be directed into the passenger compartment of the vehicle; and at least one ventilation device 100 according to the invention configured to generate an air flow FA. The enclosure 201 advantageously allows the treated air flow FA to be directed toward the passenger compartment of the vehicle. "Coolant" is understood herein to mean a fluid configured to carry calories and exchange calories with or without changing states.

As shown, the ventilation device 100 according to the invention comprises at least one casing 110 comprising at least one wall 114 defining an internal volume 210 in which at least one moving part 140, a radial thruster 120, at least one air flow FA guide member 130, and at least one air filter 113 are housed. Advantageously, the air filter 113 is arranged axially between the guide member 130 and the heat exchanger 202. The moving part 140 is configured to rotate the radial thruster 120 about the rotation axis R to generate an air flow FA, and the guide member 130 itself, together with at least a portion of the wall 114 of the casing 110, helps to straighten the air flow FA such that it has an overall direction of movement parallel to the rotation axis R of the radial thruster 120 between the air inlet 126 of the radial thruster 120 and the outlet opening formed in the wall 114 of the casing 110. As described in further detail below, at least one support 131 of the moving part 140 of the radial thruster 120 is also housed in the inner volume 210 of the housing 110 of the ventilation device, with the air flow FA guiding means 130 interposed between this support 131 and the wall 114 of the housing 110.

According to the example shown in fig. 1, the housing 110 of the ventilation device and the outer shell 201 of the system 200 are integrally formed, i.e. they form a single assembly which cannot be separated without causing damage to the housing 110 and/or the outer shell 201.

With reference to fig. 2 to 8, the ventilation device 100 according to the present invention will now be described in further detail.

Fig. 2 shows a perspective view of such a ventilation device 100, which comprises at least a housing 110 in which at least one air inlet opening 111 and one air outlet opening 112 are formed, wherein the air outlet opening 112 is at least partially closed by an air filter 113, for example. More specifically, an air inlet opening 111 and an air outlet opening 112 are formed in a wall 114 of the housing 110, respectively. Advantageously, the air filter 113 may completely close the air outlet opening 112, thereby ensuring that all air discharged from the ventilation device 100 passes through the air filter 113 before being directed to the passenger compartment of the vehicle.

According to the shown example, the ventilation device 100 extends along a main extension line D, wherein the air inlet opening 111 and the air outlet opening 112 extend in a plane parallel and perpendicular or substantially parallel and perpendicular to the main extension line D.

The casing 110, and more particularly the wall 114 of the casing 110, is generally bell-shaped, i.e. the cross-section of the casing 110 increases in size from the air inlet opening 111 towards the air outlet opening 112, when viewed in a plane perpendicular to the main extension line D of the casing 110.

As mentioned above, the wall 114 of the casing 110 defines an internal volume of the ventilation device 100 housing at least the radial thruster 120 configured to be rotated by the moving part 140 and the guide member 130 configured to direct at least part of the air flow generated by the rotation of the radial thruster 120 towards the rotation axis R of the radial thruster 120 after it passes through the guide member 130. The radial thruster 120 is rotatable by a moving member 140 housed in the support 131. For example, the moving part 140 may be an electric motor comprising at least one stator and at least one rotor, wherein the rotor is rotationally connected to a shaft accommodated in the hub 121 of the radial propeller 120. In other words, the rotation axis R of the radial thruster 120 extends parallel to the hub 121.

In fig. 2, the moving part 140 and its support 131, the radial thruster 120 and the guide member 130 are schematically shown as dashed lines. As shown, the radial thruster 120 and the guide member 130 are arranged in this order along the rotation axis R of the radial thruster 120 between the inlet opening 111 and the outlet opening 112 formed in the wall 114 of the casing 110. The guide member 130 is interposed between the moving part 140 and the wall 114 of the housing 110. More specifically, the guide member 130 is interposed between the support 131 of the moving part 140 and the wall 114 of the housing 110. "radial thruster" is understood to mean a thruster for which air enters in a direction parallel to the axis of rotation R of the thruster and exits in a direction transverse to the axis of rotation R of the thruster. As described below, the axis of rotation R of the radial thruster in the example shown is parallel to the main extension axis D of the casing 110.

The casing 110 comprises at least one upper portion 115 housing the radial thruster 120 and a lower portion 116 housing the airflow directing member 130. For example, the upper portion 115 and the lower portion 116 of the housing 110 may be unitary, i.e., they may then form a single component that cannot be separated without causing damage to at least one of the portions.

The upper portion 115 comprises at least one first portion 117, which flares towards the outlet opening 112 formed in the wall 114 of the casing 110, forming an air inlet opening 111 at the end of the at least one first portion, and at least one second portion 118, which is at least partially curved. As shown, the rotation axis of the first flared portion 117 coincides with the main extension line D of the housing 110, and the rotation axis of the second cylindrical portion 118 also coincides with the main extension line D of the housing 110. More specifically, the first portion 117 extends along a main extension line D of the casing 110 between a first end 117a where the air inlet opening 111 is formed and a second end 117b opposite to the first end 117 a. The second portion 118 itself extends along a main extension line D of the casing 110 between a first end 118a and a second end 118b opposite each other. As shown, the first end 118a of the second portion 118 and the second end 117b of the first portion 117 coincide.

The first portion 117 of the upper portion 115 of the housing 110 has a first curvature 117c extending between a first end 117a and a second end 117 b. The second portion 118 itself comprises at least one second curvature 118c extending the first portion 117, wherein the second curvature 118c is extended by a straight portion 118 d. In other words, the second curvature 118c is between the first curvature 117c of the first portion 117 and the straight portion 18d of the second portion 118. As shown, the first curvature 117c of the first portion 117 and the second curvature 118c of the second portion 118 are curved in opposite directions. In other words, the first curvature 117c of the first portion 117 is convex when viewed from the axis of rotation R of the radial thruster, and the second curvature 118c itself is concave when viewed from this axis of rotation R of the radial thruster. In other words, the first curvature 117c is inscribed in a circle having its center arranged in the environment surrounding the ventilation device according to the invention, whereas the second curvature 118c is inscribed in a circle having its center arranged in the inner volume of the ventilation device according to the invention. For example, the second curvature 118c may have a radius of curvature ranging between 23.1mm and 34.7mm measured in a plane perpendicular to the rotational axis R of the radial thruster within an angular sector of 45 °. Advantageously, the second curvature 118c has a radius of curvature equal or substantially equal to 28.9 mm. As will be described below, the second curvature 118c forms a portion of the wall 114 of the housing 110 that is configured to straighten the air flow exiting the radial thruster 120.

This results in an arrangement: wherein according to the shown example the air flow enters the ventilation device 100 via the air inlet opening 111 in a first direction and leaves the ventilation device 100 via the air outlet opening 112 in a second direction parallel or substantially parallel to the first direction. According to the example shown here, the first and second directions are also parallel to the main extension axis D of the casing 110 and therefore also to the rotation axis R of the radial thruster 120.

According to embodiments not shown here, the first curvature 117c may also be arranged to be concave when viewed from the rotational axis R of the radial thruster 120.

Fig. 3 is a perspective view of a radial thruster 120 that can be housed in the inner volume of the casing. In the rest of the description, the terms "radial impeller" and "impeller" will be used interchangeably.

The radial thruster 120 comprises a plurality of movable vanes 122 which are connected together on the one hand by a bowl 123 of the radial thruster 120 and on the other hand by an edge 124 of the radial thruster. More specifically, each movable blade 122 comprises at least one upper line 125 oriented towards an air inlet 126 of the radial thruster 120 and at least one lower line 127 oriented away from the corresponding upper line 125. The edge 124 of the radial thruster 120 connects the upper lines 125 of the movable blades 122 of the thruster 120 and the bowl 123 itself connects the lower lines 127 of the movable blades 122.

The upper line 125 of the movable vanes 122 more specifically comprises at least one first portion 125a projecting from the edge 124 towards the axis of rotation R of the thruster 120 and a second portion 125b covered in this case by the edge 124 of the thruster 120. Each movable blade 122 further comprises at least one inner edge 129 and at least one outer edge 220 connecting the upper line 125 of the movable blade 122 to the lower line 127, wherein the inner edges 129 of the movable blades 122 are oriented towards the rotation axis R of the propeller 120 and the outer edges 220 are oriented radially away from the rotation axis R.

Inner edges 129 of movable blades 122 thus define an inner perimeter P1 of impeller 120, while outer edges 220 of these movable blades 122 define an outer perimeter P2 of impeller 120. Advantageously, a portion of the impeller's rim 124 helps define an air inlet 126 of the impeller 120. According to the illustrated example, inner edge 129 of at least one of movable blades 122 forms a leading edge of propeller 120. Advantageously, the inner edge 129 of each movable blade 122 forms the leading edge of the movable blade 122 of the impeller 120.

The bowl 123 of the propeller connects the lower lines 127 of these movable blades 122. As partially shown in fig. 3, the bowl 123 is closed. In other words, each space 222 formed between two successive movable blades 122 is closed. This bowl 123 of the propeller 120 will be described in further detail below with reference to fig. 8.

As mentioned, the radial thruster 120 comprises at least an air inlet 126, via which air enters the thruster 120 in a direction parallel to the axis of rotation R of the thruster 120, and at least one radial air outlet 221, via which air exits the thruster 120 in a direction transverse to the axis of rotation R of the thruster 120. According to the example shown here, this radial air outlet 221 is formed on the outer perimeter P2 of the impeller 120, i.e. this radial air outlet 221 is axially delimited on one side by the edge 124 of the impeller 120 and on the other side by the bowl 123 of the impeller 120. In other words, at least the outer edge 220 of at least one movable vane 122 forms the trailing edge of the radial thruster 120. Advantageously, the outer edges 220 of all the movable blades 122 respectively form the trailing edge of the radial thruster 120. In case the bowl 123 of the impeller 120 is closed, it is understood that the entire air flow generated by the rotation of the impeller 120 leaves the impeller 120 via the radial air outlets 221.

Finally, according to the example shown in fig. 3, the movable blades 122 of the propeller 120 each have a curved shape, i.e. they extend in the form of a circular arc between their inner edge 129 and their outer edge 220. Advantageously, the propeller 120 may be unitary, i.e. may form a single component that cannot be separated without causing damage to the hub 121, the movable blades 122, the bowl 123 and/or the edge 124 of the propeller 120.

According to the invention, the ventilation device 100 further comprises an air flow guide member 130 capable of guiding the air flow downstream thereof towards the axis of rotation R of the radial thruster. Fig. 4 shows an embodiment of the guide member 130. More specifically, fig. 4 is a bottom perspective view of the guide member 130 shown in conjunction with a portion of the housing wall 114.

According to the example shown, the air flow guiding means 130 are radially interposed between the support 131 of the moving part and the wall 114 of the casing. The guide member 130 is more particularly formed by a plurality of fixed blades 132, which extend between the support 131 and the wall 114 of the casing, respectively. Each of these fixed blades 132 extends along a radially extending axis X between an inner end 133 in contact with the support 131 and an outer end 134 in contact with the wall 114. For example, at least one inner end 133 of one of the fixed vanes 132 is rigidly connected to the support 131, while an outer end 134 of the fixed vane 132 is rigidly connected to the wall 114. According to the example shown, all the inner ends 133 of the fixed blades 132 are rigidly connected to the support 131, and all the outer ends 134 of these fixed blades 132 are rigidly connected to the wall 114. For example, the guide member 130, the support 131 and the wall 114 of the housing may be integrally formed, i.e. they form a single assembly which cannot be separated without damaging the guide member 130, the support 131 or the wall 114.

Each stationary blade 132 also includes at least one leading edge 135 via which the airflow enters the guide member 130 and at least one trailing edge 136 via which the airflow exits the guide member 130. Thus, when the guide member 130 is in place in the housing, the leading edge 135 is oriented towards the air inlet opening formed in the housing, while the trailing edge 136 is itself oriented towards the outlet opening 112 of the housing. The leading edge 135 and the trailing edge 136 are also connected together by a pressure side 137 and by a suction side 138.

Advantageously, the fixed vanes 132 may be evenly distributed, i.e., the space 139 separating the pressure side 137 of a first fixed vane 132 from the suction side 138 of a second fixed vane 132 subsequent to the first fixed vane 132 may be equal or substantially equal in size to the space 139 separating the pressure side 137 of a second fixed vane 132 from the suction side of a third fixed vane 132 immediately subsequent to the second fixed vane 132.

As described in further detail below, each of the fixed blades 132 may almost share at least three sections S1, S2, S3 with specific features, which allows each of these fixed blades 132 to direct the air flow towards the axis of rotation of the radial propeller.

Fig. 5 to 7 show a cross section of the first portion S1 of one of the fixed blades 132, a cross section of the second portion S2 of the same fixed blade 132 and a cross section of the third portion S3 of the fixed blade 132, respectively, wherein the cross section of the first portion S1 is taken along a first transverse plane AA located at a first distance r1 from the center 230 of the guide member 130, the cross section of the second portion S2 is taken along a second transverse plane BB located at a second distance r2 from the center 230 of the guide member 130, and the cross section of the third portion S3 is taken along a third transverse plane CC located at a third distance r3 from the center 230 of the guide member 130, wherein the first transverse plane AA, the second transverse plane BB and the third transverse plane CC are each perpendicular to the radially extending axis X of the associated fixed blade 132. As shown, the first, second and third distances r1, r2, r3 are measured between the centre 230 of the guide member 130 (in this case coinciding with the centre of the support 131 of the means for moving the propeller) and the leading edge 135 of the associated fixed blade 132. According to the example shown here, the first distance r1 is equal or substantially equal to 80mm, the second distance r2 is equal or substantially equal to 90mm, and the third distance r3 is equal or substantially equal to 100mm. In other words, the first, second and third portions S1, S2, S3 of the fixed vanes 132 are aligned in this order along the radially extending axis X of the associated fixed vane 132 between the inner end 133 of the associated fixed vane 132 and the outer end 134 of the fixed vane 132.

According to the illustrated example, the first angular offset α 1, measured between a first straight line D1 passing through the leading edge 135 in the first portion S1 and a second straight line D2 passing through the leading edge 135 in the second portion S2, ranges between 2.5 ° and 4.5 °. The second angular offset α 2, measured between the second straight line D2 and a third straight line D3 passing through the leading edge 135 in the third portion S3, ranges between 3 ° and 5 °. More specifically, a first straight line D1 passes through the center 230 of the guide member and a point of the leading edge 135 of the fixed blade 132 located at a first distance r1 from the center 230 of the guide member, a second straight line D2 passes through the center 230 of the guide member and a point of the leading edge 135 of the fixed blade 132 located at a second distance r2 from the center 230, and a third straight line D3 passes through the center 230 of the guide member and a point of the leading edge 135 of the fixed blade 132 located at a third distance r3 from the center 230.

Referring to fig. 5 to 7, before providing features specific to each of the three sections S1, S2, S3, features common to the cross-section of each section will be described first.

Thus, as described above, each stationary blade 132 includes a pressure side 137 and a suction side 138 connected together by a leading edge 135 and by a trailing edge 136. It should be noted that the cross-section of the fixed blade 132 extends along the camber line C between the leading edge 135 and the trailing edge 136. This camber line C is inscribed in circles C1, C2, C3, which are schematically and partially shown as dashed lines in the figure.

The cross-section of the stationary blade 132 has a number of common dimensions. In particular, each fixed blade 132 has at least one chord line Ch and at least one maximum camber Hmax. The chord line Ch of the fixed blade 132 corresponds to a straight portion extending between the leading edge 135 and the trailing edge 136 of the fixed blade 132. According to the example shown here, the chord line Ch ranges in size from 20.2mm to 30.4 mm. The maximum camber Hmax of the fixed blade 132 itself corresponds to the dimension of this fixed blade 132 measured between the chord line Ch and the camber line C, parallel to a straight line d extending perpendicular to the chord line Ch and intersecting the camber line C, wherein the maximum camber Hmax corresponds to the maximum dimension that can be measured in this way. According to the example shown, the maximum camber Hmax ranges between 3.1mm and 4.7 mm. Further, the distance p.hmax measured between the leading edge 135 of the fixed blade 132 and the intersection point between the pressure face 137 and the straight line d perpendicular to the aforementioned chord line Ch and along which the maximum camber Hmax is measured ranges from 10mm to 15.2 mm.

The cross-section of these portions of each fixed vane 132 is also characterized by a ratio between a first angle β 1, measured between the camber line C at the leading edge 135 of the fixed vane 132 and a tangent of a circle C1, C2, C3 at the leading edge 135 of the fixed vane 132, and a second angle β 2, measured between the camber line C at the trailing edge 136 and a tangent of a circle C1, C2, C3 at the leading edge 135 of the fixed vane 132.

According to the illustrated example, the ratio between the first angle β 1 and the second angle β 2 measured in the first portion S1 ranges between 0.03 and 0.07, the ratio between the first angle β 1 and the second angle β 2 measured in the second portion S2 ranges between 0.05 and 0.12, and the ratio between the first angle β 1 and the second angle β 2 measured in the third portion S3 ranges between 0.02 and 0.07. In other words, the ratio is substantially the same in the first section S1 and the third section S3, and is greater in the second section S2.

These different ratios represent the evolution of the curvature assumed by each fixed blade 132 of the guide member 130 and allowing the air flow to be directed towards the axis of rotation of the radial thruster. The operation of the venting device 100 according to the present invention is described in further detail below with reference to fig. 8.

For example, the first angle β 1 measured in the first section S1 ranges between 4 ° and 6.2 °, and the second angle β 2 measured in the first section S2 ranges between 85 ° and 128 °. The first angle β 1 measured in the second portion S2 itself may range between 6 ° and 9.3 °, and the second angle β 2 measured in this second portion S2 ranges between 79.5 ° and 119.3 °. Finally, the first angle β 1 measured in the third section S3 ranges between 3.4 ° and 5.2 °, and the second angle β 2 measured in the third section S3 ranges between 79.4 ° and 119.3 °.

Fig. 8 shows the ventilation device 100 as a vertical cross-section taken along a vertical plane DD, such as shown in fig. 2, and thus shows the internal volume 210 of the housing 110 and the arrangement of, in particular, the impellers 120 and the air flow guiding members 130 within this internal volume 210 of the housing 110.

As mentioned above, the housing 110 extends along the main extension line D between the air inlet opening 111 and the air outlet opening 112. The air inlet opening 111, the propeller 120, the guide member 130 and the air outlet opening 112 are aligned in this order along the main extension line D of the housing 110.

The impeller 120 is more particularly arranged such that its air inlet 126 emerges at the air inlet opening 111 formed in the wall 114 of the housing 110. The support 131 of the component for moving the propeller 120 and the air guide member 130 are arranged below the propeller 120, i.e. between the propeller 120 and the air outlet opening 112, wherein the air guide member 130 is interposed between the support 131 of the moving component and the wall 114 of the housing 110. As described above, the moving parts not shown here may for example take the form of motors and may comprise drive shafts extending into the hub 121 of the propeller 120. Thus, the drive shaft rotates the hub 121, thereby rotating the entire propeller 120 and in particular the movable blades 122 of this propeller 120, so as to generate an air flow FA.

As described above, the movable blades 122 of the impeller 120 extend between the bowl 123 of the impeller 120 and the edge 124 of the impeller 120. The bowl 123 of the impeller 120 has a convex shape when viewed from the inner periphery of the impeller 120. The bowl 123 is also crossed by the hub 121 of the propeller 120, which is able to house the drive shaft of the moving part. As shown, an outer edge 220 of at least one movable vane 122 of the propeller 120 extends parallel to the rotational axis R of the propeller 120. Advantageously, the outer edges 220 of all the movable blades 122 each extend parallel to the rotation axis R of the propeller 120.

It should also be noted that inner edge 129 and outer edge 220 of each movable blade 122 have different heights and different positions. "different positions" is understood to mean that the inner edge 129 of the movable blade 122 and the outer edge 220 of this movable blade 122 have an offset with respect to one another along the axis of rotation R of the propeller 120. The "height of the edge" is understood to mean the dimension of the edge, measured parallel to the axis of rotation R of the thruster, between the bowl 123 and the edge 124 of the thruster 120. Thus, the height h1 of the inner edge 129 of the movable blade 122 of the impeller 120 is greater than the height h2 of the outer edge 220 of the impeller 120. In particular, it is possible, for example, to set the height h1 of the inner edge 129 of a movable vane 122 in the range between 36.6mm and 55mm, and to set the height h2 of the outer edge 220 of this same movable vane 122 in the range between 29mm and 44 mm. In other words, the ratio between the height h1 of the inner edge 129 of the blade and the height h2 of the outer edge 220 of the movable blade 122 ranges between 1.1 and 1.9. The impeller 120 may also be characterized by an inner radius R1, wherein the inner radius R1 is measured in a plane perpendicular to the rotational axis R of the impeller 120 between the rotational axis R of the impeller 120 and a point of the bowl 123 to the right of the inner edge 129 of one of the movable blades 122 of the impeller 120. In other words, the inner radius R1 is measured between the center of the hub 121 of the propeller 120 and the inner edge 129 of one of the movable blades 122. For example, the inner radius R1 of the impeller 120 ranges between 36mm and 54 mm. Finally, the impeller 120 has an outer radius R2, measured in a plane perpendicular to the axis of rotation R of the impeller 120, between the axis of rotation R and a point of the bowl 123 to the right of the outer edge 220 of one of the movable blades 122 of the impeller 120. For example, the outer radius R2 of the impeller 120 may range between 64mm and 96 mm.

As shown, the air flow FA enters the housing 110 via the air inlet opening 111, then enters the impeller 120 via the air inlet 126 of the impeller 120, and then exits via the radial air outlet 221 of the impeller 120. The first curvature 117c of the wall 114 of the casing 110 covers the edge 124 of the impeller 120 and the second curvature 118c of the wall 114 is arranged to face the radial air outlet 221 of the impeller 120.

The air flow FA exiting the impeller 120 thus encounters the second curvature 118c of the wall 114, causing the path of the air flow FA to change, which is thus directed towards the air flow guiding member 130. In order to allow such straightening of the air flow FA upon leaving the radial thruster 120, the second curvature 118c has, as previously described, a radius of curvature ranging between 23.1mm and 34.7mm, advantageously equal or substantially equal to 28.9 mm. The air flow FA then enters the guide member 130 via the leading edge 135 of the stationary vane 132 of the guide member. As described above, the fixed blades 132 have a particular shape that allows at least a portion of the air flow FA entering the guide member 130 to be deflected so as to be directed towards the rotation axis R of the impeller 120. The shape of these fixed vanes 132 also causes little or no deviation in another portion of the air flow through the guide members 130. In other words, it is understood that the shape of the wall 114 of the casing 110 and the shape of the fixed blades 132 of the guide member 130, together with the spaces 139 formed between successive fixed blades 132 of the guide member 130, allow the air flow FA to be guided such that the general direction of the air flow is parallel to a main extension line D of the casing 110, which in turn coincides with the rotation axis R of the impeller 120, between the air inlet 126 of the impeller 120 and the air outlet opening 112 formed in the wall 114. Advantageously, the air flow FA is thus directed over the entire surface of the air outlet opening 112, including at its center (where the rotation axis R passes), which allows the entire surface of the air filter 113 covering the air outlet opening 112 to be used, thereby improving the efficiency and durability of the air filter 113.

From the above, it can be appreciated that the present invention proposes a ventilation device in which the air flow moves in a single general direction between the air inlet of the impeller and the air outlet opening of the housing.

However, the invention is not limited to the devices and configurations described and illustrated herein, and extends to any equivalent devices and configurations, and any technically operable combinations of such devices. In particular, the shape and characteristics of the radial thrusters and of the air flow guiding members may be modified without prejudice to the invention, as long as they fulfil the functions described in this document.

Claims (12)

1. A ventilation device (100) for a vehicle heating, ventilation and/or air-conditioning system (200), comprising at least one casing (110) comprising at least one wall (114) defining an internal volume (210) in which at least one radial thruster (120) capable of being rotated and at least one guide member (130) are housed, the radial thruster (120) and the guide member (130) being configured to generate an air Flow (FA) having a general direction parallel to the axis of rotation (R) of the radial thruster (120) between an air inlet (126) of the radial thruster (120) and an air outlet opening (112) formed in the wall (114) of the casing (110) of the ventilation device (100), wherein at least a portion of the wall (114) of the casing (110) is configured to straighten the air Flow (FA) exiting the radial thruster (120), characterized in that the guide member (130) is configured to guide the air Flow (FA) towards the axis of rotation (R) of the radial thruster (120).

2. The ventilation device (100) as claimed in the preceding claim, wherein the air Flow (FA) guiding member (130) comprises a plurality of fixed blades (132) axially arranged between the radial impeller (120) and the air outlet opening (112).

3. The ventilation device (100) as claimed in the preceding claim, wherein the at least one fixed vane (132) of the air Flow (FA) guide member (130) comprises at least one outer end (134) rigidly connected to a wall (114) of the casing (110).

4. The ventilation device (100) of any one of the preceding claims, wherein the radial thruster (120) comprises a plurality of movable blades (122), wherein each movable blade (122) comprises an inner edge (129) oriented towards the axis of rotation (R) of the radial thruster (120) and an outer edge (220) oriented away from the inner edge (129), wherein at least one outer edge (220) extends parallel to the axis of rotation (R) of the radial thruster (120).

5. The ventilation device (100) according to the preceding claim, wherein an inner radius (R1) of the radial thruster (120), measured in a plane perpendicular to the axis of rotation (R) of the radial thruster (120), between the axis of rotation (R) of the radial thruster (120) and an inner edge (129) of one of the movable blades (122) of the radial thruster (120), ranges between 36mm and 54 mm.

6. The ventilation device (100) according to any one of claims 4 or 5, wherein a height (h 1) of an inner edge (129) of the movable blade (122), measured parallel to the axis of rotation (R) of the radial thruster (120), is greater than a height (h 2) of an outer edge (220) of the movable blade (122), measured parallel to the axis of rotation (R) of the radial thruster (120).

7. The ventilation device (100) according to any one of claims 2 to 6, wherein the casing (110) of the ventilation device (100) comprises at least one upper portion (115) housing the radial thruster (120) and a lower portion (116) housing the guide member (130), the upper portion (115) comprising at least one first convex curvature (117 c) when viewed from the axis of rotation (R) of the radial thruster (120) and at least one second concave curvature (118 c) when viewed from the axis of rotation (R) of the radial thruster (120), the first curvature (117 c) covering an edge (124) of the radial thruster (120), and the second curvature (118 c) being arranged facing a radial air outlet (221) of the radial thruster (120).

8. The ventilation device (100) as claimed in any of the preceding claims, wherein the air Flow (FA) guiding member (130) comprises a plurality of fixed blades (132), wherein at least one fixed blade (132) of the air Flow (FA) guiding member (130) comprises a pressure face (137) and a suction face (138) connected together by a leading edge (135) and a trailing edge (136), the fixed blade (132) comprising a cross-section extending along a camber line (C) between the leading edge (135) and the trailing edge (136) when viewed in a plane perpendicular to a radially extending axis (X) of the respective fixed blade (132), wherein the camber line (C) is inscribed within a circle (C1, C2, C3), wherein a first angle (β 1) is formed between a tangent of the circle (C1, C2, C3) at the leading edge (135) and the camber line (C) at the leading edge (135), and a second angle (79 ° in a range between the tangent of the circle (C1, C2, C3) and the leading edge (135) and the camber line (C) is in a range of 10 ° β 1 to 79 °.

9. The ventilation device (100) as claimed in the preceding claim, wherein at least one fixed vane (132) of the air Flow (FA) directing member (130) comprises a first portion (S1), a second portion (S2) and a third portion (S3), aligned in this order along a radially extending axis (X) of the vane (132) towards the wall (114) of the casing (110), wherein the ratio between the first angle (β 1) and the second angle (β 2) measured in the first portion (S1) ranges between 0.03 and 0.07, the ratio between the first angle (β 1) and the second angle (β 2) measured in the second portion (S2) ranges between 0.05 and 0.12, and the ratio between the first angle (β 1) and the second angle (β 2) measured in the third portion (S3) ranges between 0.02 and 0.07.

10. The ventilation device (100) according to any one of the preceding claims, wherein the radial thruster (120) is rotatable by at least one moving part (140), the casing (110) comprising at least one support (131) able to house the at least one part (140) for moving the radial thruster (120), and wherein the guide means (130) are interposed between the support (131) able to house the at least one moving part (140) and a wall (114) of the casing (110).

11. The ventilation device (100) according to the preceding claim, wherein the air Flow (FA) guiding member (130) comprises a plurality of fixed blades (132), and wherein at least one fixed blade (132) of the air Flow (FA) guiding member (130) comprises at least one inner end (133) rigidly connected to the support (131) capable of housing the moving part (140) and at least one outer end (134) rigidly connected to the wall (114) of the casing (110).

12. Heating, ventilation and/or air-conditioning system (200) for a vehicle, comprising at least one ventilation device (100) according to any one of the preceding claims, the system (200) comprising at least one heat exchanger (202) configured to exchange heat between the air Flow (FA) directed by the ventilation device (100) and a coolant.

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